NUMERICAL VALIDATION OF A PRESSURE-BASED BLOCK-COUPLED SOLVER FOR THE NASA ROTOR 67 TRANSONIC AXIAL COMPRESSOR CASE

The accurate simulation of highly compressible flows in turbomachinery remains a critical challenge in CFD. In high-speed axial compressors, where Mach numbers frequently exceed unity, numerical instability and sensitivity to discretization schemes often compromise the reliability. To address these issues, coupled solvers are preferred over segregated algorithms due to their superior stability and enhanced convergence for highly compressible flow. This work focuses on the validation of an implicit low dissipative pressure-based block-coupled solver available within the HELYX software, applied to the NASA Rotor 67 case. The solver proved to be robust, and the numerical results showed good agreement with experimental data, confirming its viability to solve transonic flows in turbomachinery.